CN114857086A - Axial flow compressor and gas turbine - Google Patents
Axial flow compressor and gas turbine Download PDFInfo
- Publication number
- CN114857086A CN114857086A CN202210415931.2A CN202210415931A CN114857086A CN 114857086 A CN114857086 A CN 114857086A CN 202210415931 A CN202210415931 A CN 202210415931A CN 114857086 A CN114857086 A CN 114857086A
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- inner hub
- groove
- axial
- grooves
- axial direction
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- 230000003313 weakening effect Effects 0.000 description 11
- 238000010586 diagram Methods 0.000 description 6
- 238000012545 processing Methods 0.000 description 6
- 238000012360 testing method Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 5
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000011161 development Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
Abstract
The invention discloses an axial flow compressor and a gas turbine, which comprise an outer casing, an inner hub and stator blades, wherein the outer casing is a cylinder body, and the stator blades are arranged on the inner wall of the outer casing; an inner hub disposed in the cylinder, wherein a central axis of the inner hub overlaps a central axis of the cylinder; the inner hub is provided with at least one groove, the opening of the groove faces the stator blade, the groove extends along the circumferential direction of the inner hub, and the groove is completely located in the gap between the stator blade and the inner hub along the axial direction of the inner hub. The axial flow compressor weakens the clearance leakage flow of the stator blades and improves the working efficiency of the axial flow compressor.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to an axial flow compressor and a gas turbine.
Background
An axial compressor is a turbomachinery for converting mechanical energy into pressure potential energy and generally includes an outer casing and an inner hub. In order to generate high-pressure air, the axial-flow compressor is provided with a plurality of stages of blades in the axial direction of an inner hub, a plurality of blades are fixed on the inner hub of the axial-flow compressor to form a compressor rotor, and the blades on the rotor and the inner hub rotate together and are called rotor blades. A group of static blades (stator blades for short) are arranged between two stages of rotor blades, and the stator blades play a role in rectifying working media. The group of rotor blades and the stator blades adjacent to the rear part are called as a stage of the axial flow compressor, namely, each stage of blades sequentially comprises a group of rotor blades and a group of stator blades from front to back according to the entering direction of the working medium. Wherein the stator blades are fixed on the outer casing and the rotor blades are mounted on the inner hub. The axial flow compressor works on the working medium to improve the pressure of the working medium. For light and heavy gas turbines, in order to be convenient to maintain, stator blades are not provided with stator inner ring structures, a cantilever stator form is adopted mostly, and because relative motion exists between the stator blades and an inner hub, a blade gap exists between blade tips of the stator blades and the inner hub. The blade gap is positioned in the flow channel of the working medium, and serious gap leakage flow exists. The clearance leakage flow seriously affects the working capacity of stator blades of the axial flow compressor, and further affects the margin and efficiency of components of the axial flow compressor.
Disclosure of Invention
The invention provides an axial flow compressor and a gas turbine, which are used for solving the problem that the working efficiency of the axial flow compressor is influenced due to serious leakage flow of blade gaps inside a working medium flow passage of the axial flow compressor in the prior art.
The embodiment of the invention provides an axial flow compressor, which comprises an outer casing, an inner hub and stator blades, wherein the outer casing is a cylinder, and the stator blades are arranged on the inner wall of the outer casing. The inner hub is disposed in the cylinder, and a central axis of the inner hub overlaps a central axis of the cylinder. The inner hub is provided with at least one recess opening towards the stator blade. The groove extends in the circumferential direction of the inner hub. Furthermore, the groove is located entirely in the gap between the stator blade and the inner hub in the axial direction of the inner hub.
In the embodiment, the groove in the gap between the stator blade and the inner hub weakens the leakage flow in the blade gap, and the working efficiency of the axial-flow compressor is improved. In addition, the axial flow compressor has simple processing technology and is easy to realize.
Optionally, a chord length Cd of the stator blade in the axial direction of the inner hub and a width a of the bottom of the groove in the axial direction of the inner hub satisfy: 0< a and less than or equal to 50 percent of Cd.
Optionally, the width a of the bottom of the groove in the axial direction of the inner hub and the width c of the opening of the groove in the axial direction of the inner hub satisfy: c is less than or equal to 2 a.
Optionally, the edge of one side of the stator blade close to the airflow intake direction is a leading edge, the leading edge is away from the closest groove opening by a vertical distance d from the midpoint of the axial direction of the inner hub to the leading edge, and the chord length Cd of the stator blade in the axial direction of the inner hub meets the following requirements: d is 5-40% Cd.
Optionally, the width a of the bottom of the groove along the axial direction of the inner hub and the depth b of the groove satisfy: b is more than or equal to a.
Optionally, the grooves are axisymmetric in cross section parallel to and across the central axis of the inner hub.
Optionally, the cross-section is trapezoidal or square.
Optionally, at least two grooves are axially arranged along the inner hub, and a distance e between the middle points of the openings of any two adjacent grooves along the axial direction of the inner hub and a chord length Cd of the stator blade along the axial direction of the inner hub satisfy: e is 48-52% Cd.
Optionally, the number of grooves is two. The two grooves strengthen the force for cutting off the leakage flow. Moreover, two grooves are arranged, the weakening strength of the inner hub is small, and the strength influence on the inner hub is small. Meanwhile, only two grooves are formed, so that the number is small, and the processing technology is simple.
Optionally, the groove is a slot running through the inner hub in the circumferential direction. The circumferentially through groove enables the inner hub to be opposite to the stator blade at any position, leakage flow can be cut off well, and weakening of the leakage flow is achieved.
Optionally, an edge of one side of the stator blade close to the airflow inlet direction is a leading edge, and an edge of one side close to the airflow outlet direction is a trailing edge. The groove is a circumferential non-through groove and comprises at least two sub-grooves which are distributed along the circumferential direction of the inner hub, and the length of any one of the sub-grooves along the circumferential direction of the inner hub is greater than the distance between the front edge and the rear edge along the circumferential direction of the inner hub.
Based on the same inventive concept, the application also provides a gas turbine, which comprises the axial flow compressor in any one of the technical schemes. The axial flow compressor is arranged in the groove in the gap between the stator blade and the inner hub, so that leakage flow in the gap of the blades is weakened, the working efficiency of the axial flow compressor is improved, and the overall efficiency of the gas turbine is improved.
Drawings
FIG. 1 is a schematic view of an axial compressor in the prior art;
FIG. 2 is a schematic view of an axial compressor in accordance with an embodiment of the present invention;
FIG. 3 is a schematic diagram of a groove structure of an axial compressor according to another embodiment of the present invention;
FIG. 4 is a schematic diagram of a groove structure of an axial compressor in another embodiment of the invention;
FIG. 5 is a schematic left side view of a groove in an embodiment of the present invention;
fig. 6 is a left side view of a sub-groove according to an embodiment of the present invention.
Reference numerals are as follows:
1-rotor blades; 2-stator blades;
3-an outer casing; 4-inner hub;
5-blade clearance; x-working medium;
41-groove; 411-subgroove;
410-front wall; 4100-back wall;
21-leading edge; 22-trailing edge.
Detailed Description
In order to reduce leakage flow of stator blade gaps, the embodiment of the invention provides an axial flow compressor and a gas turbine. In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail by referring to the embodiments illustrated in the accompanying drawings.
Fig. 1 is a schematic structural diagram of a prior art axial flow compressor, and as shown in fig. 1, the axial flow compressor includes an outer casing 3 and an inner hub 4, and a multi-stage blade is axially mounted on the inner hub 4, and the blade on the inner hub rotates together with the inner hub, which is called a rotor blade 1. A group of stator blades 2 are arranged between the two stages of rotor blades 1, and the stator blades 2 are used for rectifying working medium X entering the inner casing. Specifically, when the stator blade 2 is mounted, the stator blade 2 may be fixedly mounted on the outer casing 3. The axial flow compressor works on the working medium to improve the pressure of the working medium. For light and heavy gas turbines, in order to be convenient to maintain, stator blades have no stator inner ring structure, and a cantilever stator form is mostly adopted. Due to the relative movement between the stator blade and the inner hub, a blade gap 5 exists between the tip of the stator blade and the inner hub. The blade gap 5 is directly positioned in a flow channel of a working medium, so that serious leakage flow occurs in the blade gap, the working capacity of a stator blade in the axial flow compressor is influenced, and the margin and the efficiency of the axial flow compressor are further influenced.
Fig. 2 is a schematic structural diagram of an axial flow compressor in an embodiment of the invention. As shown in fig. 2, an embodiment of the present invention provides an axial compressor including an outer casing 3, an inner hub 4, rotor blades 1, and stator blades 2. The outer casing 3 is a cylinder, and the stator blades 2 are arranged on the inner wall of the outer casing 3; the inner hub 4 is provided in the cylinder, and a central axis of the inner hub 4 overlaps a central axis of the cylinder. The inner hub 4 is provided with at least one groove 41, the opening of the groove 41 is directed to the stator blade 2, the groove 41 extends along the circumferential direction of the inner hub 4, and the groove 41 is completely located at the gap between the stator blade 2 and the inner hub 4 along the axial direction of the inner hub. Specifically, the groove 41 is located right below the stator blade 2 at the position of the blade gap, and neither the front wall 410 nor the rear wall 4100 of the groove exceeds the edge of the stator blade 2 in the axial direction of the inner hub.
The working medium flows in the axial flow compressor along the axial direction of the inner hub, and the working medium can be air. The blade gap between the stator blades and the inner hub presents a leakage flow which meets the groove 41 completely in the blade gap, which will form a vortex in the groove 41, cutting off the leakage flow in the blade gap. The groove realizes weakening of leakage flow and improves the working efficiency of the axial flow compressor. And the groove processing technology of the axial flow compressor is simple and easy to realize.
Fig. 3 is a schematic diagram of a groove structure of an axial compressor in another embodiment of the invention. In a further embodiment of the present application, as shown in fig. 3, the stator blade 2 has a chord length Cd in the axial direction of the inner hub 4, which specifically refers to the length from the leading edge 21 to the trailing edge 22 at the tip of the stator blade 2. The width of the bottom of the groove 41 in the axial direction of the inner hub 4 is a. The chord length Cd and the width a meet the following conditions: 0< a and less than or equal to 50 percent of Cd.
Through test determination, when the width a and the chord length Cd meet 0< a < 50% of Cd, the leakage flow can be weakened to a greater extent. In a specific embodiment, the specific relationship between the width a and the chord length Cd is not limited in the present application, for example, the following values are adopted to achieve the purpose of the present invention, and the effect of weakening the leakage flow is achieved: a is 5% Cd; a is 10% Cd; a is 20% Cd; a is 30% Cd; a is 40% Cd; a 50% Cd.
With continued reference to fig. 3, in another alternative embodiment, the bottom of the groove 41 has a width a along the axial direction of the inner hub 4. The width of the opening of the groove 41 in the axial direction of the inner hub 4 is c. The width a of the bottom of the groove and the width c of the opening of the groove satisfy: c is less than or equal to 2 a.
Through test and determination, when the width a of the bottom of the groove 41 and the width c of the opening of the groove 41 satisfy c is less than or equal to 2a, the leakage flow can be greatly weakened. In a specific embodiment, the present application does not limit the specific relationship between the bottom width a of the groove 41 and the opening width c of the groove 41, for example, the following values can be adopted to achieve the purpose of the present invention, so as to achieve the effect of weakening the leakage flow: c is a; c is 2 a.
With continued reference to FIG. 3, in another alternative embodiment, the edge of the stator vane on the side near the direction of entry of the working medium X is the leading edge 21. The chord length of the stator blade along the axial direction of the inner hub is Cd. The opening of the groove 41 closest to the leading edge 21 is at a vertical distance d from the leading edge 21 at the midpoint in the axial direction of the inner hub. The vertical distance d between the chord length Cd and the opening midpoint of the groove and the front edge satisfies the following condition: d is 5-40% Cd.
Through test determination, when the vertical distance d between the chord length Cd and the opening midpoint of the groove and the front edge meets the condition that d is 5-40% of Cd, the leakage flow can be weakened to a large extent. In a specific embodiment, the specific relationship between the chord length Cd and the distance d is not limited in the present application, for example, the following values are adopted to achieve the purpose of the present invention, and the effect of weakening leakage flow is achieved: d is 5% Cd; d is 10% Cd; d is 15% Cd; d is 20% Cd; d is 25% Cd; d is 35% Cd; d-40% Cd.
With continued reference to fig. 3, in another alternative embodiment, the width of the bottom of the groove 41 in the axial direction of the inner hub is a. The depth of the groove 41, which refers to the vertical distance from the opening of the groove to the bottom of the groove, is b. The width a and the depth b satisfy: b is more than or equal to a.
Through test determination, when the width a and the depth b meet the condition that b is more than or equal to a, the leakage flow can be weakened to a greater degree. In a specific embodiment, the present application does not limit the specific relationship between the width a and the depth b, for example, the following values can be adopted to achieve the purpose of the present invention, so as to achieve the effect of weakening the leakage flow: b is a; b > a.
Within the range allowed by the strength of the inner hub, when the depth b of the groove is not less than the width a of the bottom of the groove, a good leakage flow weakening effect can be achieved.
In an alternative embodiment, the grooves are axisymmetric in cross section parallel to and transverse to the central axis of the inner hub. In a specific embodiment, the cross section may be semicircular, oval, triangular, or the like. The two walls of the cross section of the groove are symmetrical, so that a vortex can be well formed, and leakage flow is weakened.
Preferably, the cross-section is trapezoidal or square. Tests show that when the cross section is trapezoidal or square, the leakage flow weakening effect is best.
Fig. 4 is a schematic diagram of a groove structure of an axial compressor in another embodiment of the invention. In an alternative embodiment, as shown in fig. 4, at least two grooves 41 are arranged along the axial direction of the inner hub 4, the distance between the midpoints of the openings of any two adjacent grooves 41 along the axial direction of the inner hub is e, the chord length of the stator blade along the axial direction of the inner hub is Cd, and the opening midpoint distance e between the two grooves and the chord length Cd satisfy: e is 48-52% Cd.
Through test and determination, when the distance e between the middle points of the openings of the two grooves and the chord length Cd meet the condition that e is 48-52% of Cd, the leakage flow can be weakened to a large extent. In a specific embodiment, the specific relationship between the opening midpoint distance e and the chord length Cd of the two grooves is not limited in the present application, for example, the following values are adopted to achieve the purpose of the present invention, and the effect of weakening leakage flow is achieved: e-48% Cd; e-50% Cd; e-52% Cd.
Preferably, the number of grooves is two. At the moment, the working medium forms a vortex when passing through the first groove, the leakage flow is weakened, and then a vortex is formed in the second groove in the backward flowing process, so that the cutting-off strength of the leakage flow is enhanced. Moreover, two grooves are arranged, the weakening strength of the inner hub is small, and the strength influence on the inner hub is small. Meanwhile, only two grooves are formed, so that the number is small, and the processing technology is simple.
Fig. 5 is a left side view of a groove according to an embodiment of the present invention. In an alternative embodiment, shown in figure 5, the recess 41 is a slot running through the inner hub 4 in the circumferential direction. The circumferentially penetrating groove can cut off the leakage flow well regardless of the position of the inner hub 4 facing the stator blade, and weaken the leakage flow.
Fig. 6 is a left side view of a sub-groove according to an embodiment of the present invention. In an alternative embodiment, as shown in fig. 6, the stator blade has a leading edge 21 on the side close to the direction of the inlet of the working medium and a trailing edge 22 on the side close to the direction of the outlet of the working medium. In the present embodiment, the groove 41 is a circumferentially non-through groove, the groove 41 includes at least two sub-grooves 411 arranged along the inner circumference 4, and the length of any one of the sub-grooves 411 along the circumferential direction of the inner hub is greater than the distance between the leading edge 21 and the trailing edge 22 along the circumferential direction of the inner hub. The sub-grooves greatly weaken the leakage flow of the blade gap and improve the efficiency of the axial flow compressor.
On the whole, the circumferential groove on the surface of the inner hub is utilized to disturb the leakage flow at the blade tip position of the stator blade, and the development of the leakage flow in the axial boundary layer in the flow channel of the axial flow compressor is cut off, so that the margin of the axial flow compressor is improved, and the leakage flow is reduced. The leakage flow at the gap between the stator blade and the inner hub blade is reduced by using the circumferential groove structure on the basis of not excessively reducing the strength of the inner hub and not increasing the structural complexity of the stator blade. And the processing technology of the groove is simple, easy to realize and low in processing cost.
Embodiments of the present application also provide a gas turbine including the axial compressor in the above embodiments. The axial flow compressor has high efficiency, and the overall efficiency of the gas turbine is improved.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (12)
1. An axial flow compressor comprises an outer casing, an inner hub and stator blades, wherein the outer casing is a cylinder body, and the stator blades are arranged on the inner wall of the outer casing; the inner hub is arranged in the cylinder body, and the central shaft of the inner hub is overlapped with the central shaft of the cylinder body; characterized in that the inner hub is provided with at least one groove, the opening of the groove faces the stator blade, the groove extends along the circumferential direction of the inner hub, and the groove is completely positioned at the gap between the stator blade and the inner hub along the axial direction of the inner hub.
2. The axial compressor as recited in claim 1, wherein a chord length Cd of the stator blade in the axial direction of the inner hub and a width a of the bottom of the groove in the axial direction of the inner hub satisfy: 0< a and less than or equal to 50 percent of Cd.
3. The axial flow compressor as claimed in claim 1, wherein a width a of a bottom of the groove in the axial direction of the inner hub and a width c of an opening of the groove in the axial direction of the inner hub satisfy: c is less than or equal to 2 a.
4. The axial compressor of claim 1, wherein an edge of one side of the stator blade in the air intake direction of the air flow is a leading edge, a perpendicular distance d from a midpoint of an opening of the groove, which is closest to the leading edge, to the leading edge in the axial direction of the inner hub and a chord length Cd of the stator blade in the axial direction of the inner hub satisfy: d is 5-40% Cd.
5. The axial compressor as claimed in claim 1, wherein a width a of a bottom of the groove in an axial direction of the inner hub and a depth b of the groove satisfy: b is more than or equal to a.
6. The axial compressor as recited in claim 1, wherein a cross section of said grooves taken parallel to and through a central axis of said inner hub has an axisymmetric pattern.
7. The axial compressor according to claim 6, characterized in that said section is trapezoidal or square.
8. The axial-flow compressor according to claim 1, wherein at least two of the grooves are arranged in the axial direction of the inner hub, and a distance e between midpoints, in the axial direction of the inner hub, of openings of any two adjacent grooves and a chord length Cd of the stator blade in the axial direction of the inner hub satisfy: e is 48-52% Cd.
9. The axial compressor according to claim 1 or 8, characterized in that the number of said grooves is two.
10. The axial compressor as recited in claim 1, wherein the groove is a slot extending circumferentially through the inner hub.
11. The axial-flow compressor of claim 1, wherein the edge of the stator blade on the side close to the airflow inlet direction is a leading edge, and the edge on the side close to the airflow outlet direction is a trailing edge; the grooves are circumferentially non-through grooves, the grooves comprise at least two sub-grooves arranged along the circumferential direction of the inner hub, and the length of any one of the sub-grooves along the circumferential direction of the inner hub is greater than the distance between the leading edge and the trailing edge along the circumferential direction of the inner hub.
12. A gas turbine engine comprising an axial compressor according to any one of claims 1 to 11.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210415931.2A CN114857086A (en) | 2022-04-20 | 2022-04-20 | Axial flow compressor and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210415931.2A CN114857086A (en) | 2022-04-20 | 2022-04-20 | Axial flow compressor and gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114857086A true CN114857086A (en) | 2022-08-05 |
Family
ID=82630630
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210415931.2A Pending CN114857086A (en) | 2022-04-20 | 2022-04-20 | Axial flow compressor and gas turbine |
Country Status (1)
| Country | Link |
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| CN (1) | CN114857086A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004132209A (en) * | 2002-10-09 | 2004-04-30 | Hitachi Industries Co Ltd | Axial-flow type fluid machine |
| JP2008215275A (en) * | 2007-03-07 | 2008-09-18 | Toyota Industries Corp | Axial-flow compressor |
| US20090246007A1 (en) * | 2008-02-28 | 2009-10-01 | Erik Johann | Casing treatment for axial compressors in a hub area |
| US20100196143A1 (en) * | 2009-01-30 | 2010-08-05 | Rolls-Royce Plc | Axial compressor |
| CN101946094A (en) * | 2008-02-21 | 2011-01-12 | Mtu飞机发动机有限公司 | Circulation structure for a turbo compressor |
| CN205349788U (en) * | 2014-12-01 | 2016-06-29 | 通用电气公司 | A axial compressor end wall is handled for controlling wherein leakage stream |
| CN111322272A (en) * | 2020-03-31 | 2020-06-23 | 中国科学院工程热物理研究所 | Front narrow and rear wide type seam type casing processing device for gas compressor |
| US20200248575A1 (en) * | 2019-02-06 | 2020-08-06 | United Technologies Corporation | Spiraling grooves as a hub treatment for cantilevered stators in compressors |
-
2022
- 2022-04-20 CN CN202210415931.2A patent/CN114857086A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004132209A (en) * | 2002-10-09 | 2004-04-30 | Hitachi Industries Co Ltd | Axial-flow type fluid machine |
| JP2008215275A (en) * | 2007-03-07 | 2008-09-18 | Toyota Industries Corp | Axial-flow compressor |
| CN101946094A (en) * | 2008-02-21 | 2011-01-12 | Mtu飞机发动机有限公司 | Circulation structure for a turbo compressor |
| US20090246007A1 (en) * | 2008-02-28 | 2009-10-01 | Erik Johann | Casing treatment for axial compressors in a hub area |
| US20100196143A1 (en) * | 2009-01-30 | 2010-08-05 | Rolls-Royce Plc | Axial compressor |
| CN205349788U (en) * | 2014-12-01 | 2016-06-29 | 通用电气公司 | A axial compressor end wall is handled for controlling wherein leakage stream |
| US20200248575A1 (en) * | 2019-02-06 | 2020-08-06 | United Technologies Corporation | Spiraling grooves as a hub treatment for cantilevered stators in compressors |
| CN111322272A (en) * | 2020-03-31 | 2020-06-23 | 中国科学院工程热物理研究所 | Front narrow and rear wide type seam type casing processing device for gas compressor |
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